EP0146624B1 - Vorgang für die intensivierung des thermoenergetischen zyklus und strahltriebwerke - Google Patents

Vorgang für die intensivierung des thermoenergetischen zyklus und strahltriebwerke Download PDF

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Publication number
EP0146624B1
EP0146624B1 EP84902846A EP84902846A EP0146624B1 EP 0146624 B1 EP0146624 B1 EP 0146624B1 EP 84902846 A EP84902846 A EP 84902846A EP 84902846 A EP84902846 A EP 84902846A EP 0146624 B1 EP0146624 B1 EP 0146624B1
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EP
European Patent Office
Prior art keywords
fuel
blades
air
turbine
cooling
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
EP84902846A
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English (en)
French (fr)
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EP0146624A4 (de
EP0146624A1 (de
Inventor
Marius A. Paul
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PAUL Marius A
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Individual
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Filing date
Publication date
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Priority to AT84902846T priority Critical patent/ATE41476T1/de
Publication of EP0146624A1 publication Critical patent/EP0146624A1/de
Publication of EP0146624A4 publication Critical patent/EP0146624A4/de
Application granted granted Critical
Publication of EP0146624B1 publication Critical patent/EP0146624B1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/16—Composite ram-jet/turbo-jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This invention concerns a method of increasing the efficiency and output of a gas-turbine which has turbine blades with internal passages for cooling the blades by supplying the internal passages with a cooling fluid and which has a combustion chamber for combustion of fuel with the combustion gases driving the turbine blades.
  • a gas-turbine of this type is disclosed in U.S. specification No. 2,647,368.
  • the object of the invention is to provide a gas- turbine engine which is capable of operating at high pressures and temperatures utilising the total expansion of the generated gases without the size, weight and complexity customarily associated with such engines, and without the need to use exotic materials, such as ceramics.
  • the present invention provides a method of increasing the efficiency and output of a gas- turbine of the type mentioned in the first paragraph hereto, said method being characterised by arranging the combustion chamber annularly around the turbine blades, cooling the gas-turbine blades with a mixture of air and liquid-fuel introduced internally into the blades, wherein the liquid-fuel vaporizes to form an air-fuel mixture, expelling the air-fuel vapour mixture directly from the blades into the annular combustion chamber for turbulent mixing and combustion, combusting the air-fuel vapour mixture in the combustion chamber and directing the gases of combustion at the same turbine blades to drive the gas-turbine.
  • This invention puts an end to the above difficulties because it assures the cooling of the blades of the gas-turbines and of all the hot surfaces by fluids and air in an open recuperative circuit, allowing the increased cooling at a thermodynamic (stoichiometric) maximum of the temperature of the burnt-gases, which pass through the turbine.
  • the cooling fluids together with the air form rich mixtures with great convective capacity in the cooling system.
  • the cooling fluids may be constituted of petroleum-fuels or of liquified gases, such as liquid hydrogen or liquid methane, or of methanol.
  • liquified gases such as liquid hydrogen or liquid methane, or of methanol.
  • the turbine blades extend radially from a disk and some quantity of the cooling fluid (liquid fuel) is bi-laterally injected onto the turbine disk, where a film coating is produced which is centrifuged toward the turbine-blades gases.
  • the interior and exterior of the blades are cooled by introduction of the cooling fuel from the film coating together with air into the internal channels in the blades where the cooling fuel vaporizes, thus providing convective evaporative cooling.
  • the resultant air-fuel vapour mixture is then centrifugally and tangentially expelled into the combustion chamber.
  • cooling fluid liquid fuel
  • the cooling fluid liquid fuel
  • the combustion chamber located at the periphery of the turbine and around it, creates a turbo-recuperative space, where the rich mixture made up of the combustible cooling fluids emulsified with air is expelled with the peripheral speed of the turbine-rotor such as 400m/sec. This assures a high level of peripheral turbulence and results in a final stoichiometric mixture of maximal quality.
  • the combustion chamber of the gas-turbine is supplied with fuel from a direct source by individual injectors and also with the emulsion of air and fuel which cooled the turbine.
  • the recirculation of the cooling air to the combustion chamber has a recuperative effect and the utilization of the same air for combustion eliminates the previous quantitative restriction on cooling-air.
  • the turbo-engine shown in the drawing is made up of a gas-turbine including an interior compressor-rotor 1, with axial blades, associated with an interior radial compressor-rotor 2, having interposed an exterior compressor-rotor 3, with axial blades, and an exterior radial compressor-rotor 4.
  • An air-duct 5 leads the compressed-air to an air-housing 6, which contains an annular peripheral combustion-chamber 7 provided with exterior meridian air-ports 8 and with interior meridian air-ports 9.
  • a turbine-rotor 10 is provided with blades with conventional air-cooling ducts. The blades are mounted on a turbine-disk 11 and are cooled by liquid-injectors 12.
  • a second stage gas-turbine rotor 14 actuates the interior axial and radial compressors 1, 2, while the turbine 10 actuates the exterior axial and radial compressors 3, 4.
  • a further turbine 15 is the final stage of using the energy.
  • the combustion chamber 7 is provided with primary fuel injectors 16.
  • the entire rotary- assembly is supported via bearings 17,18,19, 20, 21, 22.
  • Stator blades 23 and 24 of final turbines 14 and 15 are adjustable for optimizing the speed- regime.
  • the walls 25 and 26 of the combustion-chamber 7 are manufactured with perforations 100, which allow inlet of air over the whole metal surface of the combustion-chamber 7, and include supplementary air inlets 27, disposed for assuring high quality combustion.
  • the operation of the gas-turbine, according to the invention and to the drawing is assured by counter-rotary driving of the interior compressor 1, with axial blades, and of the interior compressor with radial blades 2 and by driving of the exterior axial compressor 3 and of the exterior radial compressor 4, which pumps the air up through the duct 5 into the air-housing 6, which contains the annular chamber 7.
  • Combustion is assured by injecting primary fuel through the injectors 16 and this allows the start of the gas- turbine and its working at reduced power. At high power, cooling of the blades becomes necessary when the burnt gases surpass 1000-1200°C.
  • the injectors 12 then inject cooling liquid-fuel which settles on the turbine-disk 11 in film form, radially penetrates into the interior channels of the blades of the rotor 10 and together with the cooling-air forms an emulsion having a high capacity for absorption of heat from the blade walls.
  • the fuel vapour from the cooling-liquid and the air that passes through the interior channels of the blades of the turbines 10, are expelled radially and tangentially into the annular, peripheral combustion-chamber 7, where, by final mixing, they completely burn at a level of stoichiometric limit.
  • the whole flow passage of the burnt gases is manufactured of perforated sheet with micro- orifices on the whole surface. This allows air perspiration, which eliminates material contact between the metal-walls and the burnt-gases.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
  • Percussion Or Vibration Massage (AREA)
  • Means For Warming Up And Starting Carburetors (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Claims (11)

1. Verfahren zur Erhöhung der Effizienz und Leistungsabgabe einer Gasturbine, die Turbinenschaufeln (10) mit inneren Kanälen zur Kühlung der Schaufeln aufweist, indem den inneren Kanälen eine Kühlflüssigkeit zugeführt wird, und die eine Brennkammer (7) für die Verbrennung von Kraftstoff aufweist, wobei die Verbrennungsgase die Turbinenschaufeln (10) antreiben, gekennzeichnet durch die Anordnung der Brennkammer (7) ringförmig um die Turbinenschaufeln (10), das Kühlen der Gasturbinenschaufeln (10) mit einem innen in die Schaufeln eingeführten Gemisch aus Luft und Flüssigkraftstoff, wobei der Flüssigkraftstoff verdampft, um ein Luft-Kraftstoff-Gemisch zu bilden, das Austreiben des Luft-Kraftstoffdampfgemischs zur turbulenten Vermischung und Verbrennung direkt von den Schaufeln (10) aus in die ringförmige Brennkammer, die Verbrennung des Luft-Kraftstoffdampfgemischs in der Brennkammer und das Beaufschlagen derselben Turbinenschaufeln (10) mit den Verbrennungsgasen zum Antrieb der Gasturbine.
2. Verfahren nach Anspruch 1 unter Verwendung von Schaufeln (10), die radial von einer Scheibe (11) ausgehen, und weiter gekennzeichnet durch das Einspritzen des Flüssigkraftstoffs auf die Turbinenscheibe (11), um eine Filmbeschichtung zu bilden, die gegen die Schaufeln (10) geschleudert wird, wobei die Innenseite und die Außenseite der der Schaufeln mit dem Kühlkraftstoff gekühlt werden, indem der Kühlkraftstoff von der Filmbeschichtung zusammen mit Luft in die inneren Kanäle in den Schaufeln eingeführt wird, wo der Kühlkraftstoff in ein Luft-Kraftstoffdampfgemisch verdampft, und wobei der radiale und tangentiale Ausstoß des Luft-Kraftstoffdampfgemischs von den Schaufeln direkt in die Brennkammer erfolgt, wodurch die während der Kühlens absorbierte Wärme in die Brennkammer eingeführt wird.
3. Verfahren nach Anspruch 1 oder 2, einschließend das Einblasen von zusätzlicher Luft in die Brennkammer (7) an einer Vielzahl von Stellen (8) rund um den Außenumfang der Kammer.
4. Verfahren nach Anspruch 1, 2 oder 3, einschließend das Mischen des emittierten Luft-Kraftstoffdampfgemischs mit zusätzlicher Luft und Kraftstoff zur Beaufschlagung der Brennkammer, um eine stöchiometrische Verbrennung zu erzielen.
5. Verfahren nach irgendeinem der vorstehenden Ansprüche, wobei die Brennkammer (7) den Ausstoß der Verbrennung auf die Schaufeln (10) der Gasturbine lenkende Kammerwände (25, 26) aufweist.
6. Verfahren nach Anspruch 5, wobei die Kammerwände Perforationen (100) aufweisen, die ein Kühlen der Wände durch Einblasen von Luft durch die Perforationen ermöglichen.
7. Verfahren nach irgendeinem der vorstehenden Ansprüche, wobei die Gasturbine einen zusammenwirkenden Verdichter (1, 3) aufweist, und weiterhin einschließend das Zuführen der nach innen in die Schaufeln (10) eingeblasenen Luft unter Druck vom Verdichter (1, 3).
8. Verfahren nach irgendeinem der vorstehenden Ansprüche, wobei der Flüssigkraftstoff bei Umgebungstemperaturen und -drücken ein Gas ist, das durch Druck und/oder abgesenkte Temperatur verflüssigt wird.
9. Verfahren nach irgendeinem der vorstehenden Ansprüche, wobei als Flüssigkraftstoff Wasserstoff verwendet wird.
10. Verfahren nach einem der Ansprüche 1 bis 8, wobei als Flüssigkraftstoff Methan verwendet wird.
11. Verfahren nach einem der Ansprüche 1 bis 7, wobei als Flüssigkraftstoff Methanol verwendet wird.
EP84902846A 1983-06-20 1984-06-20 Vorgang für die intensivierung des thermoenergetischen zyklus und strahltriebwerke Expired EP0146624B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT84902846T ATE41476T1 (de) 1983-06-20 1984-06-20 Vorgang fuer die intensivierung des thermoenergetischen zyklus und strahltriebwerke.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US50565883A 1983-06-20 1983-06-20
US505658 1983-06-20

Publications (3)

Publication Number Publication Date
EP0146624A1 EP0146624A1 (de) 1985-07-03
EP0146624A4 EP0146624A4 (de) 1986-03-18
EP0146624B1 true EP0146624B1 (de) 1989-03-15

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EP84902846A Expired EP0146624B1 (de) 1983-06-20 1984-06-20 Vorgang für die intensivierung des thermoenergetischen zyklus und strahltriebwerke

Country Status (9)

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EP (1) EP0146624B1 (de)
JP (1) JPS60501616A (de)
AU (1) AU3210384A (de)
BR (1) BR8406943A (de)
CA (1) CA1235583A (de)
DE (1) DE3477229D1 (de)
DK (1) DK77385A (de)
IT (1) IT1177817B (de)
WO (1) WO1985000199A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19902437C5 (de) * 1999-01-22 2017-01-12 General Electric Technology Gmbh Verfahren und Vorrichtung zum schnellen Anfahren und zur schnellen Leistungssteigerung einer Gasturbinenanlage

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4858428A (en) * 1986-04-24 1989-08-22 Paul Marius A Advanced integrated propulsion system with total optimized cycle for gas turbines
US4916896A (en) * 1988-11-02 1990-04-17 Paul Marius A Multiple propulsion with quatro vectorial direction system
FR2670869B1 (fr) * 1990-12-19 1994-10-21 Snecma Chambre de combustion comportant deux enceintes successives.
JP2988109B2 (ja) * 1991-03-20 1999-12-06 株式会社日立製作所 回転電機用ロータシャフト及びそれを用いた回転電機
GB9418949D0 (en) * 1994-09-20 1994-11-09 Helliwell Brian J 90% thermal efficient gas turbine engine
EP2622192A2 (de) * 2010-09-30 2013-08-07 General Electric Company Flugzeugtriebwerksysteme und verfahrenfür ihren betrieb
JP6031097B2 (ja) * 2011-06-17 2016-11-24 ゼネラル・エレクトリック・カンパニイ 航空機エンジン燃料システム及びその作動方法
US9709069B2 (en) 2013-10-22 2017-07-18 Dayspring Church Of God Apostolic Hybrid drive engine
JP7250304B2 (ja) * 2018-09-26 2023-04-03 国立大学法人室蘭工業大学 タービン駆動用ガスジェネレータの推進剤及びその製造方法

Citations (1)

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US2647368A (en) * 1949-05-09 1953-08-04 Hermann Oestrich Method and apparatus for internally cooling gas turbine blades with air, fuel, and water

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Publication number Priority date Publication date Assignee Title
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19902437C5 (de) * 1999-01-22 2017-01-12 General Electric Technology Gmbh Verfahren und Vorrichtung zum schnellen Anfahren und zur schnellen Leistungssteigerung einer Gasturbinenanlage

Also Published As

Publication number Publication date
DE3477229D1 (en) 1989-04-20
BR8406943A (pt) 1985-06-04
CA1235583A (en) 1988-04-26
DK77385D0 (da) 1985-02-20
AU3210384A (en) 1985-01-25
JPS60501616A (ja) 1985-09-26
EP0146624A4 (de) 1986-03-18
IT8448432A0 (it) 1984-06-20
DK77385A (da) 1985-02-20
EP0146624A1 (de) 1985-07-03
WO1985000199A1 (en) 1985-01-17
IT1177817B (it) 1987-08-26

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